2008-06-20: Fuel tank system

2008-06-20 Fokker Services B.V.: Amendment 39-15432. Docket No. FAA- 2007-29030; Directorate Identifier 2006-NM-284-AD. Effective Date (a) This airworthiness directive (AD) becomes effective April 23, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Fokker Model F.28 Mark 0070 and 0100 airplanes, all serial numbers, certificated in any category; and Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes, serial numbers 11003 through 11241, 11991 and 11992, certificated in any category. Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (g)(1) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane. Subject (d) Transport Association (ATA) of America Code 28: Fuel. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA published Special Federal Aviation Regulation 88 (SFAR 88) in June 2001. SFAR 88 required a safety review of the aircraft Fuel Tank System to determine that the design meets the requirements of FAR (Federal Aviation Regulation) Sec. 25.901 and Sec. 25.981(a) and (b). A similar regulation has been recommended by the JAA (Joint Aviation Authorities) to the European National Aviation Authorities in JAA letter 04/00/02/07/03-L024 of 3 February 2003. The review was requested to be mandated by NAA's (National Aviation Authorities) using JAR (Joint Aviation Regulation) Sec. 25.901(c), Sec. 25.1309. In August 2005 EASA published a policy statement on the process for developing instructions for maintenance and inspection of Fuel Tank System ignition source prevention (EASA D 2005/CPRO, http:// www.easa.eu.int/home/cert_policy_statements_en.html) that also included the EASA expectations with regard to compliance times of the corrective actions on the unsafe and the not unsafe part of the harmonised design review results. On a global scale the TC (type certificate) holders committed themselves to the EASA published compliance dates (see EASA policy statement). The EASA policy statement has been revised in March 2006: The date of 31-12-2005 for the unsafe related actions has now been set at 01-07-2006. Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' as defined in FAA's memo 2003- 112-15 `SFAR 88--Mandatory Action Decision Criteria'. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements. This EASA Airworthiness Directive mandates the Fuel System Airworthiness Limitations, comprising maintenance/inspection tasks and Critical Design Configuration Control Limitations (CDCCL) for the type of aircraft, that resulted from the design reviews and the JAA recommendation and EASA policy statement mentioned above. The corrective action includes revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness for certain airplanes, and the FAA-approved maintenance program for certain other airplanes, to incorporate new limitations for fuel tank systems. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 3 months after the effective date of this AD or before December 16, 2008, whichever occurs first, do the action in paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as applicable. For all identified tasks, the initial compliance time starts from the effective date of this AD. The repetitive inspections must be accomplished thereafter at the intervals not to exceed those specified in Fokker 70/100 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-672, Issue 2, dated December 1, 2006; or Fokker Service Bulletin SBF28-28-050, Revision 1, dated January 8, 2008; as applicable; except as provided by paragraphs (f)(3), (f)(4), and (g)(1) of this AD. (i) For Model F.28 Mark 0070 and 0100 airplanes: Revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate the inspections, thresholds, and intervals specified in Fokker 70/100 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-672, Issue 2, dated December 1, 2006. (ii) For Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes: Incorporate into the FAA-approved maintenance inspection program the inspections, thresholds, and intervals specified in Fokker Service Bulletin SBF28-28-050, Revision 1, dated January 8, 2008. (2) Within 3 months after the effective date of this AD or before December 16, 2008, whichever occurs first, do the action in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, as applicable. (i) For Model F.28 Mark 0070 and 0100 airplanes: Revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate the CDCCLs as defined in Fokker 70/100 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-672, Issue 2, dated December 1, 2006, except for the CDCCL component titled "Level Control Pilot Valve Solenoid, jiffy junction.'' (ii) For ModelF.28 Mark 1000, 2000, 3000, and 4000 airplanes: Incorporate into the FAA-approved maintenance inspection program the CDCCLs as defined in Fokker Service Bulletin SBF28-28-050, Revision 1, dated January 8, 2008. (3) Where Fokker 70/100 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-672, Issue 2, dated December 1, 2006; and Fokker Service Bulletin SBF28-28-050, Revision 1, dated January 8, 2008; allow for exceptional short-term extensions, an exception is acceptable to the FAA if it is approved by the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (4) After accomplishing the actions specified in paragraphs (f)(1) and (f)(2) of this AD, no alternative inspection, inspection interval, or CDCCL may be used, unless the inspection, interval, or CDCCL is part of a later revision of Fokker 70/100 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-672, Issue 2, dated December 1, 2006; or Fokker Service Bulletin SBF28-28-050, Revision 1, dated January 8, 2008; as applicable; that is approved by the Manager, ANM-116, International Branch, Transport Airplane Directorate, FAA, or the European Aviation Safety Agency (EASA), or its delegated agent, or unless the inspection, interval, or CDCCL is approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (g)(1) of this AD. (5) Actions done before the effective date of this AD in accordance with Fokker 70/100 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-672, Issue 1, dated January 31, 2006; or Fokker Service Bulletin F28/28-050, dated June 30, 2006; are acceptable for compliance with the corresponding requirements of this AD. Note 2: For Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes, after an operator complies withthe requirements of paragraphs (f)(1)(ii) and (f)(2)(ii) of this AD, those paragraphs do not require that operators subsequently record accomplishment of those requirements each time an applicable action is accomplished according to that operator's FAA-approved maintenance inspection program. FAA AD Differences Note 3: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120- 0056. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2006-0206, dated June 11, 2006; EASA Airworthiness Directive 2006-0208, dated July 12, 2006; Fokker 70/ 100 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-672, Issue 2, dated December 1, 2006; and Fokker Service Bulletin SBF28-28-050, Revision 1, dated January 8, 2008; for related information. Material Incorporated by Reference (i) You must use Fokker 70/100 Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) Report SE-672, Issue 2, dated December 1, 2006; and Fokker Service Bulletin SBF28-28-050, Revision 1, dated January 8, 2008; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr- locations.html.